초록
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A flight control method and system for a rotary wing aircraft. When the longitudinal speed UX of the aircraft is greater than a first threshold speed Vthresh1, a first mode of operation of the method enables flight to be performed while maintaining track relative to the ground, the flight setpoints of an autopilot being a ground course angle TKsol, a forward speed Va, a flight path angle P, and a heading Ψ. When the longitudinal speed UX is less than a second threshold speed Vthresh2, a second mode of operation enables flight to be performed while mainta...
A flight control method and system for a rotary wing aircraft. When the longitudinal speed UX of the aircraft is greater than a first threshold speed Vthresh1, a first mode of operation of the method enables flight to be performed while maintaining track relative to the ground, the flight setpoints of an autopilot being a ground course angle TKsol, a forward speed Va, a flight path angle P, and a heading Ψ. When the longitudinal speed UX is less than a second threshold speed Vthresh2, a second mode of operation enables flight to be performed while maintaining heading, the flight setpoints being the longitudinal speed UX, a lateral speed VY, a vertical speed WZ, and the heading Ψ.
대표
청구항
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1. A flight control method for a rotary wing aircraft, the aircraft following a track Tsol relative to the ground with a forward speed Va, a longitudinal direction X extending from the rear of the aircraft to the front of the aircraft, an elevation direction Z extending upwards perpendicularly to the longitudinal direction X, and a transverse direction Y extending from left to right perpendicularly to the longitudinal and elevation directions X and Z, the aircraft comprising: at least one rotary wing having a plurality of main blades of collective pitch ...
1. A flight control method for a rotary wing aircraft, the aircraft following a track Tsol relative to the ground with a forward speed Va, a longitudinal direction X extending from the rear of the aircraft to the front of the aircraft, an elevation direction Z extending upwards perpendicularly to the longitudinal direction X, and a transverse direction Y extending from left to right perpendicularly to the longitudinal and elevation directions X and Z, the aircraft comprising: at least one rotary wing having a plurality of main blades of collective pitch and cyclic pitch that are variable about respective pitch axes, the aircraft being capable of performing movements in rotation about the directions X, Y, Z and of performing movements in translation along the directions X, Y, Z;an autopilot that generates control signals in predefined modes of operations and in application of flight setpoints, the control signals being capable of causing the aircraft to perform the movements in rotation and/or in translation relative to the directions X, Y, Z; andflight controls having at least one control member provided jointly with a plurality of movement axes A, B, C, D;the method comprising the following steps: applying a first mode of operation of the control members and of the autopilot when the longitudinal speed UX of the aircraft is greater than a first threshold speed Vthresh1, the longitudinal speed UX being a projection of the forward speed Va onto the longitudinal direction X, the autopilot then enabling the aircraft to fly while maintaining track relative to the ground, the flight setpoints of the autopilot being a ground course angle TKsol, the forward speed Va, a flight path angle P, and a heading Ψ; andapplying a second mode of operation for the control members and the autopilot when the longitudinal speed UX is less than a second threshold speed Vthresh2, the first threshold speed Vthresh1 being greater than the second threshold speed Vthresh2, the autopilot then enabling the aircraft to fly while maintaining heading, the flight setpoints of the autopilot being the longitudinal speed UX, a lateral speed VY, a vertical speed WZ, and the heading Ψ. 2. A flight control method according to claim 1 for a rotary wing aircraft, wherein: the first mode of operation of the control members and of the autopilot remains engaged so long as the longitudinal speed UX is greater than or equal to the second threshold speed Vthresh2; andthe second mode of operation of the control members and of the autopilot remains engaged so long as the longitudinal speed UX is less than or equal to the first threshold speed Vthresh1. 3. A flight control method according to claim 1 for a rotary wing aircraft, wherein during the first mode of operation of the control members and of the autopilot: in order to enable the aircraft to follow a new track Tsoln, it is possible by transparency to modify: the forward speed Va by a first action relative to a first movement axis A of a control member and by means of the autopilot;the ground course angle TKsol by a second action relative to a second movement axis B of a control member and by means of the autopilot; and/orthe flight path angle P by a third action relative to a third movement axis C of a control member and by means of the autopilot; andthe flight setpoints of the autopilot are aligned on the parameters of the new track Tsoln, the flight setpoints being a new ground course angle TKsol, a new forward speed Van, a new flight path angle Pn, and/or a new heading Ψ in order to enable the autopilot to follow the new track Tsoln. 4. A flight control method according to claim 3 for a rotary wing aircraft, wherein during the first mode of operation of the control members and of the autopilot: in order to cause the aircraft to follow a new track Tsoln, it is possible by transparency to modify the ground course angle TKsol relative to the ground by a fourth action relative to a fourth movement axis D of a control member and by means of the autopilot; andthe flight setpoints of the autopilot are aligned on the new parameters of the new track Tsoln on a new ground course angle TKsoln in order to enable the autopilot to follow the new track Tsoln. 5. A flight control method according to claim 1 for a rotary wing aircraft, wherein if the forward speed Va is less than a third threshold speed Vthresh3, the flight path angle P is replaced by the vertical speed WZ as the flight setpoint of the autopilot in the first mode of operation of the control members and of the autopilot. 6. A flight control method according to claim 1 for a rotary wing aircraft, wherein the second mode of operation of the control members and of the autopilot: in order to enable the aircraft to follow a new track Tsoln, it is possible by transparency and independently to modify: the longitudinal speed UX by a first action relative to a first movement axis A of a control member and by means of the autopilot;the lateral speed VY by a first action relative to a second movement axis B of a control member and by means of the autopilot; and/orthe vertical speed WZ by a third action relative to a third movement axis C of a control member and by means of the autopilot; andthe flight setpoints of the autopilot are aligned on: a new longitudinal speed UXn of the aircraft if the new longitudinal speed UXn is greater than a fourth threshold speed Vthresh4; anda new lateral speed VYn of the aircraft if the new lateral speed VYn has an absolute value that is less than a fifth threshold speed Vthresh5. 7. A flight control method according to claim 1 for a rotary wing aircraft, wherein in the second mode of operation of the control members and of the autopilot: in order to enable the aircraft to follow a new track Tsoln, it is possible by transparency and independently to modify: the longitudinal speed UX by a first action relative to a first movement axis A of a control member and by means of the autopilot;the lateral speed VY by a second action relative to a second movement axis B of a control member and by means of the autopilot; and/orthe vertical speed WZ by a third action relative to a third movement axis C of a control member and by means of the autopilot; andthe flight setpoints of the autopilot are aligned on: a new longitudinal speed UXn of the aircraft if the new longitudinal speed UXn is greater than a fourth threshold speed Vthresh4; anda new lateral speed VYn of the aircraft after the pilot of the aircraft performs a specific action. 8. A flight control method according to claim 6 for a rotary wing aircraft, wherein in the second mode of operation of the control members and of the autopilot, the flight setpoints of the autopilot are aligned on a new vertical speed WZn of the aircraft if the new vertical speed WZn has an absolute value that is greater than a sixth threshold speed Vthresh6. 9. A flight control method according to claim 6 for a rotary wing aircraft, wherein in the second mode of operation of the control members and of the autopilot: it is possible by transparency to modify the heading Ψ by a fourth action relative to a fourth movement axis D of a control member and by means of the autopilot, independently of the speed UX, VY, WZ; andthe flight setpoint of the autopilot corresponding to the heading Ψ of the aircraft is aligned on a new heading Ψn. 10. A flight control method according to claim 6, for a rotary wing aircraft, wherein: if the new longitudinal speed UXn has an absolute value that is less than a seventh threshold speed Vthresh7, the flight setpoint corresponding to the longitudinal speed UX is zero; andif the new lateral speed VYn has an absolute value that is less than the seventh threshold speed Vthresh7, the flight setpoint corresponding to the lateral speed UY is zero. 11. A flight control method according to claim 1 for a rotary wing aircraft, wherein the first and second threshold speeds Vthresh1, Vthresh2 are a function of the longitudinal speed of the relative wind to which the aircraft is subjected and of the lateral speed VY. 12. A flight control method according to claim 1 for a rotary wing aircraft, wherein the aircraft has firstly a first control lever for controlling movements in rotation of the aircraft about the longitudinal and transverse directions X and Y, and secondly a second control lever for controlling movements of the aircraft in translation along the elevation direction Z, and a first control member is the first control lever, and a second control member is the second control lever, the first control member having the first movement axis A and the second movement axis B, the second control member having the third movement axis C. 13. A flight control method according to claim 12 for a rotary wing aircraft, wherein a violent action on the first control lever causes the autopilot to deactivate maintaining the flight path angle setpoint P, the first control lever then controlling movements in rotation of the aircraft about the longitudinal direction X, and the second control lever controlling movements in translation of the aircraft along the elevation direction Z. 14. A flight control method according to claim 1 for a rotary wing aircraft, wherein the aircraft has firstly a first control lever for controlling movements in rotation of the aircraft about the longitudinal and transverse directions X and Y, and secondly a second control lever enabling movements of the aircraft in translation to be controlled along the elevation direction Z, and a first control member is positioned on the first control lever and a second control member is positioned on the second control lever, the first control member having the first movement axis A and the second movement axis B, and the second control member having the third movement axis C. 15. A flight control method according to claim 14 for a rotary wing aircraft, wherein the second control member has a fourth movement axis D. 16. A flight control method according to claim 1 for a rotary wing aircraft, wherein the control members are calibrated and control precise movements of the aircraft. 17. A flight control method according to claim 1 for a rotary wing aircraft, wherein the flight setpoints of the autopilot can be varied in order to cause the aircraft to engage hovering flight towards a stop position S that is determined on applying the engagement of hovering flight for the aircraft. 18. A flight control system for a rotary wing aircraft, the aircraft following a track Tsol relative to the ground with a forward speed Va, a longitudinal direction X extending from the rear of the aircraft to the front of the aircraft, an elevation direction Z extending upwards perpendicularly to the longitudinal direction X, and a transverse direction Y extending from left to right perpendicularly to the longitudinal and elevation directions X and Z: the aircraft comprising at least one rotary wing having a plurality of main blades of collective pitch and cyclic pitch that are variable about respective pitch axes, the aircraft being capable of performing movements in rotation about the directions X, Y, Z and of performing movements in translation along the directions X, Y, Z;the flight control system comprising: at least one control member provided jointly with a plurality of movement axes A, B, C, D; andan autopilot that generates control signals in predefined modes of operation and in application of flight setpoints, the control signals being capable of causing the aircraft to perform the movements in rotation and/or in translation relative to the directions X, Y, Z; andwherein the flight control system performs the flight control method according to claim 1 for a rotary wing aircraft.
